CN107451354A - A kind of emulation mode and terminal device of canard configuration rudders pneumatic power parameter - Google Patents
A kind of emulation mode and terminal device of canard configuration rudders pneumatic power parameter Download PDFInfo
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Abstract
The present invention is applied to vehicle technology field, there is provided a kind of emulation mode and terminal device of canard configuration rudders pneumatic power parameter, including：Build the threedimensional model of canard configuration aircraft；Surface to the threedimensional model of the canard configuration aircraft and flow field domain corresponding to the threedimensional model of the canard configuration aircraft carry out mesh generation, and the volume mesh in flow field domain is obtained according to the grid on the overseas surface of the grid on threedimensional model surface and flow field；Establish the k ε turbulent flow mathematical modelings simulated to the air flow inside volume mesh；Analog approach is carried out to the aerodynamic parameter of canard configuration aircraft by k ε turbulent flows mathematical modelings.This programme is by building the threedimensional model of canard configuration aircraft, then according to the threedimensional model of aircraft obtain corresponding to flow field domain volume mesh, the aerodynamic parameter that simulation obtains aircraft is carried out to the gas inside the volume mesh around aircraft by turbulent flow mathematical modeling, this method cycle is short, cost is small, and emulation mode is accurate.
Description
Technical field
The invention belongs to vehicle technology field, more particularly to a kind of emulation mode of canard configuration rudders pneumatic power parameter
And terminal device.
Background technology
With the development of trajectory message acquiring technology, ballistic deflection technology for eliminating, rocket projectile is progressively by without control or simple steering
Overall trajectory Guidance and control develops, meanwhile, the attack precision of rocket projectile also steps up.Rocket projectile realizes that the premise of precision strike is
With preferable aerodynamic configuration, in existing guided rocket bullet, widely used aerodynamic configuration is added in forebody
Duck rudder is filled, fin is used in afterbody.
Relative to uncontrolled missile, the change of duck rudder and empennage can make its aerodynamic characteristic produce larger change, be accurate
The aerodynamic characteristic of canard configuration guided rocket bullet is obtained, the method for the existing aerodynamic characteristic for calculating rocket projectile is typically to use wind
Hole is tested, but wind tunnel experiment cost is big, cycle length.
The content of the invention
In view of this, the embodiments of the invention provide a kind of emulation mode and terminal of canard configuration rudders pneumatic power parameter
Equipment, for being emulated to the aerodynamic parameter of canard configuration aircraft, so as to calculate the pneumatic ginseng of canard configuration aircraft
Number.
The first aspect of the embodiment of the present invention provides a kind of emulation mode of canard configuration rudders pneumatic power parameter, bag
Include：
Build the threedimensional model of canard configuration aircraft；
The threedimensional model on surface and the canard configuration aircraft to the threedimensional model of the canard configuration aircraft
The outer surface in corresponding flow field domain carries out mesh generation, according to the net on the overseas surface of the grid on the threedimensional model surface and flow field
Lattice obtain the volume mesh in the flow field domain, and the volume mesh is the grid model of the canard configuration aircraft；
Establish the k- ε turbulent flow mathematical modelings simulated to the air flow inside the volume mesh；
Analog approach is carried out to the aerodynamic parameter of the canard configuration aircraft by the k- ε turbulent flows mathematical modeling.
The second aspect of the embodiment of the present invention provides a kind of terminal device, including：
Model construction module, for building the threedimensional model of canard configuration aircraft；
Mesh generation module, surface and the canard configuration for the threedimensional model to the canard configuration aircraft
The outer surface in flow field domain corresponding to the threedimensional model of aircraft carries out mesh generation, according to the grid on the threedimensional model surface and
The grid on the overseas surface in flow field obtains the volume mesh in the flow field domain, and the volume mesh is the grid of the canard configuration aircraft
Model；
Turbulence model creation module, for establishing the k- ε turbulent flows simulated to the air flow inside the volume mesh
Mathematical modeling；
Aerodynamic parameter analog module, for the gas by the k- ε turbulent flows mathematical modeling to the canard configuration aircraft
Dynamic parameter carries out analog approach.
The third aspect of the embodiment of the present invention provides a kind of terminal device, including memory, processor and is stored in
In the memory and the computer program that can run on the processor, described in the computing device during computer program
The step of realizing the methods described that first aspect of the embodiment of the present invention provides.
The fourth aspect of the embodiment of the present invention provides a kind of computer-readable recording medium, the computer-readable storage
Media storage has computer program, and the computer program realizes the embodiment of the present invention when being executed by one or more processors
On the one hand the step of methods described provided.
Existing beneficial effect is the embodiment of the present invention compared with prior art：
By the threedimensional model for building canard configuration aircraft；To the surface of the threedimensional model of the canard configuration aircraft
And the outer surface in flow field domain corresponding to the threedimensional model of the canard configuration aircraft carries out mesh generation, according to the three-dimensional
The grid on the overseas surface of the grid of model surface and flow field obtains the volume mesh in the flow field domain, and the volume mesh is the canard
The grid model of layout aircraft；Establish the k- ε turbulent flow mathematical modelings simulated to the air flow inside the volume mesh；
Analog approach is carried out to the aerodynamic parameter of the canard configuration aircraft by the k- ε turbulent flows mathematical modeling, the present invention need not
Analog approach is carried out to the aerodynamic parameter of canard configuration aircraft by wind tunnel experiment can, reduces cost, the cycle is short.
Brief description of the drawings
Technical scheme in order to illustrate the embodiments of the present invention more clearly, below will be to embodiment or description of the prior art
In the required accompanying drawing used be briefly described, it should be apparent that, drawings in the following description be only the present invention some
Embodiment, for those of ordinary skill in the art, without having to pay creative labor, can also be according to these
Accompanying drawing obtains other accompanying drawings.
Fig. 1 is a kind of emulation mode implementation process for canard configuration rudders pneumatic power parameter that one embodiment of the invention provides
Schematic diagram；
Fig. 2 is the three-dimensional model diagram for the canard configuration aircraft that one embodiment of the invention provides；
Fig. 3 is the flow field domain for the aircraft that one embodiment of the invention provides；
Fig. 4 is the flow field domain grid schematic diagram that one embodiment of the invention provides；
Fig. 5 is the aircraft surface grids schematic diagram that one embodiment of the invention provides；
Fig. 6 is Vehicle nose's surface grids schematic diagram that one embodiment of the invention provides；
Fig. 7 is the aircraft afterbody surface grids schematic diagram that one embodiment of the invention provides；
Fig. 8 is the boundary layer volume mesh schematic diagram that one embodiment of the invention provides；
Fig. 9 is the schematic block diagram for the terminal device that one embodiment of the invention provides；
Figure 10 is the schematic block diagram for the terminal device that one embodiment of the invention provides.
Embodiment
In describing below, in order to illustrate rather than in order to limit, it is proposed that such as tool of particular system structure, technology etc
Body details, thoroughly to understand the embodiment of the present invention.However, it will be clear to one skilled in the art that there is no these specific
The present invention can also be realized in the other embodiments of details.In other situations, omit to well-known system, device, electricity
Road and the detailed description of method, in case unnecessary details hinders description of the invention.
It should be appreciated that ought be in this specification and in the appended claims in use, special described by the instruction of term " comprising "
Sign, entirety, step, operation, the presence of element and/or component, but be not precluded from one or more of the other feature, entirety, step,
Operation, element, component and/or its presence or addition for gathering.
It is also understood that the term used in this description of the invention is merely for the sake of the mesh for describing specific embodiment
And be not intended to limit the present invention.As used in description of the invention and appended claims, unless on
Other situations are hereafter clearly indicated, otherwise " one " of singulative, "one" and "the" are intended to include plural form.
It will be further appreciated that the term "and/or" used in description of the invention and appended claims is
Refer to any combinations of one or more of the associated item listed and be possible to combine, and including these combinations.
As used in this specification and in the appended claims, term " if " can be according to context quilt
Be construed to " when ... " or " once " or " in response to determining " or " in response to detecting ".Similarly, phrase " if it is determined that " or
" if detecting [described condition or event] " can be interpreted to mean according to context " once it is determined that " or " in response to true
It is fixed " or " once detecting [described condition or event] " or " in response to detecting [described condition or event] ".
In order to illustrate technical solutions according to the invention, illustrated below by specific embodiment.
Fig. 1 is that a kind of emulation mode for canard configuration rudders pneumatic power parameter that one embodiment of the invention provides realizes stream
Journey schematic diagram, as shown in the figure this method may comprise steps of：
Step S101, build the threedimensional model of canard configuration aircraft.
In embodiments of the present invention, in order to obtain the pneumatic ginseng of canard configuration aircraft by way of computer simulation
Number is, it is necessary to first build the threedimensional model of aircraft, the canard configuration aircraft can be canard configuration rocket projectile.
As one embodiment, Fig. 2 is the outline drawing for the canard configuration aircraft that one embodiment of the invention uses, described
Canard configuration aircraft is specially：
, as prototype, to install four duck rudders additional without control aircraft in Vehicle nose and obtain canard configuration aircraft；
The structure of four duck rudders is identical；
The duck rudder enters horizontal deflection in flight course according to control instruction；
Empennage deploys after rocket ejection gun tube and is fixedly connected with body to fold fin.
It should be noted that the embodiment of the present invention is using certain type active service rocket projectile as prototype, including 4 duck rudders, body and 6
Piece empennage, it is fixedly connected between the empennage and body；4 duck rudders are evenly distributed on the head of body, and away from bullet top
Apart from identical；6 empennages are evenly distributed on the afterbody of body；In flight course, four duck rudders can be according to Guidance and control
The throw of pointer, so as to form controling power and control moment, and then realize projectile correction.The dimensional units of the threedimensional model are
Mm, the overall length of the threedimensional model is 5700mm.The head of rocket projectile uses karman curve profile.If body can also be set
A diameter of D, then the overall length of guided rocket bullet is 22D, and the embodiment of above rocket projectile is only intended to illustrate, and can also be other and flies
Row device, corresponding threedimensional model can also be set according to specific aircraft in a particular application, the threedimensional model is basis
The geometric shape of actual aircraft obtains.
Step S102, surface and the canard configuration aircraft to the threedimensional model of the canard configuration aircraft
The outer surface in flow field domain corresponding to threedimensional model carries out mesh generation, overseas according to the grid on the threedimensional model surface and flow field
The grid on surface obtains the volume mesh in the flow field domain, and the volume mesh is the grid model of the canard configuration aircraft.
In embodiments of the present invention, it is necessary to establish flow field domain to the canard configuration aircraft, Fig. 3 is to the canard cloth
The flow field domain of office's aircraft structure, the flow field domain is the atmosphere around aircraft, and the flow field domain is one and contained
The region of cylinder including aircraft, the axis and body or aircraft of the cylinder are coaxial, the air in the region
Flowing can influence the aerodynamic parameter of aircraft.If the length of aircraft is L, a diameter of D, the both sides in flow field domain and the head of aircraft
The distance of portion and afterbody is respectively 2L and 4L, and the diameter in flow field domain is the diameter of 90 times of aircraft, i.e. 90D can also basis
Actual conditions reset diameter, length and both sides and the head of aircraft and the distance of afterbody in flow field domain.Actually should
In, it is other shapes that can also set flow field domain, but flow field domain must be the region being enclosed in around aircraft.
, it is necessary to flow field to the canard configuration aircraft after flow field domain corresponding to the canard configuration aircraft is established
Domain carries out mesh generation, obtains the grid model of the canard configuration aircraft.The grid model of the canard configuration aircraft
It can obtain in the following manner：
The threedimensional model on surface and the canard configuration aircraft to the threedimensional model of the canard configuration aircraft
The outer surface in corresponding flow field domain carries out mesh generation, according to the net on the overseas surface of the grid on the threedimensional model surface and flow field
Lattice obtain the volume mesh in the flow field domain, and the volume mesh is the grid model of the canard configuration aircraft.
In embodiments of the present invention, it is necessary first to surface and flow field domain to the threedimensional model of canard configuration aircraft it is outer
Surface carries out mesh generation, and then the grid on the overseas surface of the grid further according to threedimensional model surface and flow field obtains the flow field
The volume mesh in domain.
Specifically, including：
According to the three-dimension modeling flow field domain of the canard configuration aircraft；
The threedimensional model pair on surface and the canard configuration aircraft to the threedimensional model of the canard configuration aircraft
The outer surface in the flow field domain answered carries out mesh generation respectively, obtains the face on the overseas surface of surface grids and flow field on threedimensional model surface
Grid, the surface grids on the threedimensional model surface are full gore grid, and the surface grids on the threedimensional model surface include：Head
Portion's surface grids, duck rudder face grid, bomb body surface grids and the part of empennage surface grids four；
Volume mesh, the volume mesh bag are generated according to the surface grids on the overseas surface of the surface grids on threedimensional model surface and flow field
Include tetrahedral grid two parts outside prism boundary layer hexahedral mesh and boundary layer；
Totally ten layers of prism boundary layer hexahedral mesh, four sides outside prism boundary layer hexahedral mesh and boundary layer
The growth ratio of volume mesh is 1.2；
If the minimum volume of any volume mesh is more than zero, the grid model of the canard configuration aircraft is obtained.
In embodiments of the present invention, first need, according to three-dimension modeling flow field domain, then to enter the surface of threedimensional model
Row mesh generation obtains the surface grids of aircraft three-dimensional model, and then same mode obtains the surface grids on the overseas surface in flow field,
Due to the special structure of aircraft, the surface grids on threedimensional model surface include：Surface grids, the duck rudder face net of Vehicle nose
The surface grids of lattice, aircraft surface grids in itself and empennage, the full-size of head surface grids is 15mm, and duck rudder face grid is most
Large scale is 6mm, and the full-size of aircraft body surface grids is 20mm, and the full-size of empennage surface grids is 8mm, the stream
The surface grids full-size of field domain outer surface is 1500mm, if the aircraft is rocket projectile, the surface grids of aircraft in itself
Thrum dignity grid.These surface grids are merged into generation volume mesh, the volume mesh of generation is exactly canard configuration aircraft
Grid model.The volume mesh includes tetrahedral grid two parts outside prism boundary layer hexahedral mesh and boundary layer, described
Prism boundary layer hexahedral mesh is close to body outer surface；Prism boundary layer hexahedral mesh shares 10 layers.Finally, also need
Check whether that the minimum volume of all volume mesh is both greater than 0, if both greater than 0, the grid model obtained is exactly the duck
The grid model of formula layout aircraft.If the volume mesh for thering is volume to be less than or equal to 0, then need to repartition grid until
The minimum volume of all volume mesh is both greater than 0.Fig. 4 and Fig. 5 is ready-portioned flow field domain grid schematic diagram and aircraft respectively
Veil trrellis diagram.The a diameter of 90D in flow field domain in Fig. 4, peripheral distance of the Vehicle nose apart from head side flow field domain is 2L, flight
Peripheral distance of the empennage of device apart from empennage side flow field domain is 4L, and the above is also only one of citing, is not used to limit
The system present invention.
Fig. 6 is that head surface grids enlarged diagram, Fig. 7 of aircraft in Fig. 5 are that aircraft afterbody surface grids amplify in Fig. 5
Schematic diagram, Fig. 8 are boundary layer volume mesh sectional views.
As one embodiment of the invention, mesh generation is carried out in the following manner：
According to formulaThe height Δ y of first layer grid is obtained, wherein, Δ y is the height of first layer grid,
ρ is gas density, and μ is molecular viscosity coefficient, τwFor wall shear stress, y+It is worth for the self-defining value in 30~300；Obtaining
After first layer grid height Δ y, the face of prism boundary layer six is obtained with according to first layer grid height and grid growth ratio
Tetrahedral grid outside volume mesh and boundary layer.Work as y+Comparatively ideal result of calculation and convergence rate can be obtained in 30-300.
The first layer grid height of prism boundary layer hexahedral mesh is corresponding with the vehicle flight speeds simulated, when institute's mould
When the flying speed of plan is 0.6Ma, 0.8Ma, 1.0Ma, 1.2Ma, 1.5Ma, 2.0Ma, 2.5Ma, 3.0Ma, 3.5Ma, 4.0Ma,
Its corresponding first layer grid highly be respectively 0.12078mm, 0.093mm, 0.0762mm, 0.06472mm, 0.0528mm,
0.0408mm、0.0334mm、0.0282mm、0.0246mm、0.0219mm、0.0197mm、0.0180mm；The prism boundary layer
The grid that the 1st to the 10th layer of hexahedral mesh is highly increased in 1.2 ratio.Prism boundary layer hexahedral mesh can be obtained respectively
With tetrahedral grid outside boundary layer.
Step S103, establish the k- ε turbulent flow mathematical modelings simulated to the air flow inside the volume mesh.
In embodiments of the present invention, establish on the basis of the eddy viscosity assumption of isotropy, the k- ε turbulent flow mathematical modelings
Specially：
Tubulence energy k equations：
The rule that dissipates ε equations：
In formula：K is tubulence energy, and t represents time, ρ gas densities, and μ is molecular viscosity coefficient, turbulent viscosity
Cμ=0.0845, xiAnd xjDenotation coordination component, ε are tubulence energy dissipative shock wave respectively, GkAnd GbRespectively by local velocity gradient and
Tubulence energy generating item caused by wind-force, YMFor the dissipative shock wave that expansion fluctuation is formed in compressible turbulent flow, C1ε、C2ε、C3εIt is normal for experience
Number, respectively C1ε=1.5, C2ε=2.1, G3ε=0.1, σkAnd σεThe respectively turbulent prandtl number corresponding with k and ε, respectively
For σk=1.1, σε=1.4, SkAnd SεFor customized source item, respectively Sk=Sε=0.
The k- ε turbulent flows mathematical modeling is used to simulate the air flow around the canard configuration aircraft three-dimensional model,
Because the surface there is provided the flow field domain of canard configuration aircraft, and to canard configuration aircraft and flow field domain have carried out grid
Division, that is to say, that per individual net in flow field domain of the k- ε turbulent flows mathematical modeling for simulating the canard configuration aircraft
Air flow inside lattice.This is also equivalent to air flow actual around aircraft in wind tunnel experiment.
Step S104, mould is carried out to the aerodynamic parameter of the canard configuration aircraft by the k- ε turbulent flows mathematical modeling
Intend solving.
In embodiments of the present invention, the air flow around canard configuration aircraft is entered by k- ε turbulent flows mathematical modelings
Row simulation, it is possible to the pneumatic ginseng of canard configuration aircraft is calculated by the air flow around canard configuration aircraft
Number, the aerodynamic parameter include：Resistance coefficient, lift coefficient, rolling moment coefficient.
It is that the three-dimensional solver based on the implicit stable state of density is used for k- ε turbulent flow mathematical modelings that we, which set solver, first
Solve, the vehicle flight speeds of simulation are 2.5 Mach (Ma), and its Reynolds number order of magnitude is 107.In actual applications, may be used also
To set the different flying speed of aircraft, so as to simulate the aerodynamic parameter under different flying speeds.Mach number is certain in flow field
Point speed with the local velocity of sound of the point ratio, that is, represent velocity of sound multiple numerical value, be a dimensionless number, one Mach
Number represents one times of velocity of sound.
Then also need to set the primary condition and boundary condition of the grid model of canard configuration aircraft.
Specific primary condition and boundary condition are：
The external boundary condition for setting the flow field domain is pressure far field；
Air pressure inside the flow field domain is arranged to 101325pa, and the temperature setting inside the domain of flow field is 300K, flow field domain
Internal flowing material is perfect gas；
The specific heat capacity of the perfect gas varies with temperature, and temperature change unit is 100-1000, by range of temperature
Be divided into 8 stages, the specific heat capacity of the fluent material corresponding to this 8 stages is respectively 1161, -2.4,0.015, -5.03e-05、
9.9e-08、-1.1e-10、6.5e-14、-1.6e-17。
The boundary condition on the surface of the canard configuration aircraft is arranged to stable without sliding wall；
The rotary rpm in the flow field domain is set to 0rad/s.
After there is provided the primary condition of canard configuration aircraft and boundary condition, it is possible to k- ε turbulent flow mathematical modelings
Solve, carried out in embodiments of the present invention, during to the k- ε turbulent flows mathematics model solution by way of iterative.This is just
Need first to set solution control parameter：Residual error convergence is 10-5, iterations 5000, ginseng is controlled by the solution of setting
It is several to k- ε turbulent flow mathematical modeling iteratives, obtain the flow velocity of the flow velocity, i.e. air flow of turbulent motion, pass through the air
The flow velocity can of flowing calculates the rolling moment coefficient for obtaining canard configuration aircraft.Specific solution control parameter can also
It is configured according to the situation of reality, for example, it is also possible to set discrete scheme (single order upstreame scheme, Second-order Up-wind form) to be used for
Precision in solution procedure is set, the area that area of reference is bomb body cross section can also be set, defining reference density is
1.176671Kg/m3 definition reference length is 1m；The precision that iteration in each step-length can also be set is 2, can also set rapids
The relaxation factor of kinetic energy is 0.4, and it is 0.5 to set turbulent dissipation relaxation factor, and it is 0.4 to set turbulent viscosity relaxation factor.
After being emulated, can also once it be emulated again, as initial emulation, this emulation can for emulation before
To set the iterations of simulation calculation, as 5000, other parameters do corresponding adjustment according to actual conditions, are solved for example, setting
Courant Number be 2, the relaxation factor for setting tubulence energy is 0.4, and it is 0.5 to set turbulent dissipation relaxation factor, is set
Turbulent viscosity relaxation factor is 0.4.
It should be noted that arrangement above is also only used for illustrating, in actual applications, can also set different residual
Poor convergence, different iterationses etc..
The embodiment of the present invention sets different size of mesh opening to different parts, can effectively reduce the total number of grid, subtract
Small follow-up amount of calculation, shorten and calculate the time, meanwhile, it is capable to ensure that the air flows such as projectile nose, duck rudder, empennage are complex
Effectively simulated at position；Different size of mesh opening is designed according to different flying speeds, it can be ensured that different flying speeds
In the case of the aerodynamic parameter that is obtained it is more accurate；The setting of calculating parameter is able to ensure that obtained aerodynamic parameter meets reality
Border flight progress；First carry out primary Calculation and be able to ensure that in calculating process not producing result of calculation dissipates, and further calculates energy
Enough ensure that residual values are not produced in calculating process does not reach convergence or the pseudo-convergent situation of result of calculation；Utilize the present invention
Aerodynamic coefficient is carried out, can quickly obtain the aerodynamic parameter of accurate canard configuration aircraft, and cost is far below wind-tunnel
Experiment；The present invention passes through wind tunnel test data verification, can ensure the accuracy of result of calculation.
It should be understood that the size of the sequence number of each step is not meant to the priority of execution sequence, each process in above-described embodiment
Execution sequence should determine that the implementation process without tackling the embodiment of the present invention forms any limit with its function and internal logic
It is fixed.
Fig. 9 is the schematic block diagram for the terminal device that one embodiment of the invention provides, and for convenience of description, is only shown and this hair
The related part of bright embodiment.
The terminal device can be the list of the software unit, hardware cell or the soft or hard combination that are built in terminal device
Member, it can also be integrated into as independent suspension member in the terminal device.
The terminal device 9 includes：
Model construction module 91, for building the threedimensional model of canard configuration aircraft；
Mesh generation module 92, surface and the canard cloth for the threedimensional model to the canard configuration aircraft
The outer surface in flow field domain carries out mesh generation corresponding to the threedimensional model of office's aircraft, according to the grid on the threedimensional model surface
The volume mesh in the flow field domain is obtained with the grid on the overseas surface in flow field, the volume mesh is the net of the canard configuration aircraft
Lattice model；
Turbulence model creation module 93, it is rapid for establishing the k- ε simulated to the air flow inside the volume mesh
Flow mathematical modeling；
Aerodynamic parameter analog module 94, for by the k- ε turbulent flows mathematical modeling to the canard configuration aircraft
Aerodynamic parameter carries out analog approach.
According to the content in the embodiment of the emulation mode of corresponding canard configuration rudders pneumatic power parameter, the terminal is set
It is standby to include other modules or unit, it is numerous to list herein.
It is apparent to those skilled in the art that for convenience of description and succinctly, only with above-mentioned each work(
Can module division progress for example, in practical application, can be as needed and by above-mentioned function distribution by different functions
Module is completed, will the internal structure of the terminal device be divided into different functional modules, to complete whole described above
Or partial function.Each functional module in embodiment can be integrated in a processing module or modules list
Solely it is physically present, can also be in Cheng Yi module of two or more modules, above-mentioned integrated module can both use hard
The form of part is realized, can also be realized in the form of software function module.In addition, the specific name of each functional module is also
For the ease of mutually distinguishing, the protection domain of the application is not limited to.The specific work process of module in said system, can
With reference to the corresponding process in preceding method embodiment, will not be repeated here.
Description in other modules corresponding with emulation mode or unit reference emulation mode embodiment, herein no longer
Repeat.
Figure 10 is the schematic block diagram for the terminal device that one embodiment of the invention provides.As shown in Figure 10, the end of the embodiment
End equipment 10 includes：One or more processors 100, memory 101 and it is stored in the memory 101 and can be described
The computer program 102 run on processor 100.The processor 100 is realized above-mentioned each when performing the computer program 102
Step in individual emulation mode embodiment, such as the step S101 to S104 shown in Fig. 1.Or the processor 100 performs institute
The function of each module in above-mentioned simulator embodiment, such as module 91 to 94 shown in Fig. 9 are realized when stating computer program 102
Function.
Exemplary, the computer program 102 can be divided into one or more module/units, it is one or
Multiple module/the units of person are stored in the memory 101, and are performed by the processor 100, to complete the present invention.Institute
It can be the series of computation machine programmed instruction section that can complete specific function to state one or more module/units, the instruction segment
For describing implementation procedure of the computer program 102 in the server 10.For example, the computer program 102 can
To be divided into model construction module, mesh generation module, turbulence model creation module, aerodynamic parameter analog module.
Model construction module, for building the threedimensional model of canard configuration aircraft；
Mesh generation module, surface and the canard configuration for the threedimensional model to the canard configuration aircraft
The outer surface in flow field domain corresponding to the threedimensional model of aircraft carries out mesh generation, according to the grid on the threedimensional model surface and
The grid on the overseas surface in flow field obtains the volume mesh in the flow field domain, and the volume mesh is the grid of the canard configuration aircraft
Model；
Turbulence model creation module, for establishing the k- ε turbulent flows simulated to the air flow inside the volume mesh
Mathematical modeling；
Aerodynamic parameter analog module, for the gas by the k- ε turbulent flows mathematical modeling to the canard configuration aircraft
Dynamic parameter carries out analog approach.
Description in other modules corresponding with emulation mode or unit reference emulation mode embodiment, herein no longer
Repeat.
The terminal device includes but are not limited to processor 100, memory 101.It will be understood by those skilled in the art that
Figure 10 is only the example of terminal device 10, does not form the restriction to terminal device 10, can be included more more or more than illustrating
Few part, either combines some parts or different parts, for example, the terminal device can also include input equipment,
Output equipment, network access equipment, bus etc..
The processor 100 can be CPU (Central Processing Unit, CPU), can also be
Other general processors, digital signal processor (Digital Signal Processor, DSP), application specific integrated circuit
(Application Specific Integrated Circuit, ASIC), ready-made programmable gate array (Field-
Programmable Gate Array, FPGA) either other PLDs, discrete gate or transistor logic,
Discrete hardware components etc..General processor can be microprocessor or the processor can also be any conventional processor
Deng.
The memory 101 can be the internal storage unit of the terminal device 10, such as the hard disk of terminal device 10
Or internal memory.The memory 101 can also be the External memory equipment of the terminal device 10, such as on the terminal device 10
The plug-in type hard disk of outfit, intelligent memory card (Smart Media Card, SMC), secure digital (Secure Digital, SD)
Card, flash card (Flash Card) etc..Further, the memory 101 can also be both interior including the terminal device 10
Portion's memory cell also includes External memory equipment.The memory 101 is used to store the computer program and the terminal
Other programs and data needed for equipment.The memory 101, which can be also used for temporarily storing, have been exported or will be defeated
The data gone out.
In the above-described embodiments, the description to each embodiment all emphasizes particularly on different fields, and is not described in detail or remembers in some embodiment
The part of load, it may refer to the associated description of other embodiments.
Those of ordinary skill in the art are it is to be appreciated that the list of each example described with reference to the embodiments described herein
Member and algorithm steps, it can be realized with the combination of electronic hardware or computer software and electronic hardware.These functions are actually
Performed with hardware or software mode, application-specific and design constraint depending on technical scheme.Professional and technical personnel
Described function can be realized using distinct methods to each specific application, but this realization is it is not considered that exceed
The scope of the present invention.
In embodiment provided by the present invention, it should be understood that disclosed terminal device and emulation mode, Ke Yitong
Other modes are crossed to realize.For example, device described above/terminal device embodiment is only schematical, for example, described
The division of module or unit, only a kind of division of logic function, can there is other dividing mode when actually realizing, such as more
Individual unit or component can combine or be desirably integrated into another system, or some features can be ignored, or not perform.It is another
Point, shown or discussed mutual coupling or direct-coupling or communication connection can be by some interfaces, device or
The INDIRECT COUPLING of unit or communication connection, can be electrical, mechanical or other forms.
The unit illustrated as separating component can be or may not be physically separate, show as unit
The part shown can be or may not be physical location, you can with positioned at a place, or can also be distributed to multiple
On NE.Some or all of unit therein can be selected to realize the mesh of this embodiment scheme according to the actual needs
's.
In addition, each functional unit in each embodiment of the present invention can be integrated in a processing unit, can also
That unit is individually physically present, can also two or more units it is integrated in a unit.Above-mentioned integrated list
Member can both be realized in the form of hardware, can also be realized in the form of SFU software functional unit.
If the integrated module/unit realized in the form of SFU software functional unit and as independent production marketing or
In use, it can be stored in a computer read/write memory medium.Based on such understanding, the present invention realizes above-mentioned implementation
All or part of flow in example method, by computer program the hardware of correlation can also be instructed to complete, described meter
Calculation machine program can be stored in a computer-readable recording medium, and the computer program can be achieved when being executed by processor
The step of stating each embodiment of the method..Wherein, the computer program includes computer program code, the computer program
Code can be source code form, object identification code form, executable file or some intermediate forms etc..Computer-readable Jie
Matter can include：Can carry any entity or device of the computer program code, recording medium, USB flash disk, mobile hard disk,
Magnetic disc, CD, computer storage, read-only storage (ROM, Read-Only Memory), random access memory (RAM,
Random Access Memory), electric carrier signal, telecommunication signal and software distribution medium etc..It is it should be noted that described
The content that computer-readable medium includes can carry out appropriate increasing according to legislation in jurisdiction and the requirement of patent practice
Subtract, such as in some jurisdictions, according to legislation and patent practice, computer-readable medium do not include be electric carrier signal and
Telecommunication signal.
Embodiment described above is merely illustrative of the technical solution of the present invention, rather than its limitations；Although with reference to foregoing reality
Example is applied the present invention is described in detail, it will be understood by those within the art that：It still can be to foregoing each
Technical scheme described in embodiment is modified, or carries out equivalent substitution to which part technical characteristic；And these are changed
Or replace, the essence of appropriate technical solution is departed from the spirit and scope of various embodiments of the present invention technical scheme, all should
Within protection scope of the present invention.
Claims (10)
- A kind of 1. emulation mode of canard configuration rudders pneumatic power parameter, it is characterised in that including：Build the threedimensional model of canard configuration aircraft；The threedimensional model on surface and the canard configuration aircraft to the threedimensional model of the canard configuration aircraft is corresponding Flow field domain outer surface carry out mesh generation, obtained according to the grid on the overseas surface of the grid on the threedimensional model surface and flow field To the volume mesh in the flow field domain, the volume mesh is the grid model of the canard configuration aircraft；Establish the k- ε turbulent flow mathematical modelings simulated to the air flow inside the volume mesh；Analog approach is carried out to the aerodynamic parameter of the canard configuration aircraft by the k- ε turbulent flows mathematical modeling.
- 2. according to the method for claim 1, it is characterised in that the canard configuration aircraft is canard configuration rocket projectile, The threedimensional model of the canard configuration aircraft is specially：, as prototype, to install four duck rudders additional without control aircraft in Vehicle nose and obtain canard configuration aircraft；The structure of four duck rudders is identical；The duck rudder enters horizontal deflection in flight course according to control instruction；The empennage of aircraft afterbody deploys after rocket ejection gun tube and is fixedly connected with body to fold fin.
- 3. according to the method for claim 1, it is characterised in that the threedimensional model to the canard configuration aircraft The outer surface in flow field domain corresponding to the threedimensional model of surface and the canard configuration aircraft carries out mesh generation, according to described The volume mesh that the grid on the overseas surface of the grid on threedimensional model surface and flow field obtains the flow field domain includes：According to the three-dimension modeling flow field domain of the canard configuration aircraft；Surface to the threedimensional model of the canard configuration aircraft and corresponding to the threedimensional model of the canard configuration aircraft The outer surface in flow field domain carries out mesh generation respectively, obtains the veil on the overseas surface of surface grids and flow field on threedimensional model surface Lattice, the surface grids on the threedimensional model surface are full gore grid, and the surface grids on the threedimensional model surface include：Head Surface grids, duck rudder face grid, bomb body surface grids and the part of empennage surface grids four；Volume mesh is generated according to the surface grids on the overseas surface of the surface grids on threedimensional model surface and flow field, the volume mesh includes rib Tetrahedral grid two parts outside post boundary layer hexahedral mesh and boundary layer, totally ten layers of prism boundary layer hexahedral mesh, The growth ratio of tetrahedral grid is 1.2 outside prism boundary layer hexahedral mesh and boundary layer；The height Δ y of prism boundary layer first layer grid is obtained by below equation：<mrow> <msup> <mi>y</mi> <mo>+</mo> </msup> <mo>=</mo> <mfrac> <mrow> <mi>&Delta;</mi> <mi>y</mi> <mi>&rho;</mi> </mrow> <mi>&mu;</mi> </mfrac> <msqrt> <mfrac> <msub> <mi>&tau;</mi> <mi>w</mi> </msub> <mi>&rho;</mi> </mfrac> </msqrt> </mrow>Wherein, Δ y is the height of prism boundary layer first layer grid, and ρ is gas density, μ molecular viscosity coefficients, τwCut for wall Stress, y+It is worth for the self-defining value in 30~300；According to prism boundary layer first layer grid height Δ y and grid growth ratio, prism boundary layer hexahedron can be obtained respectively Tetrahedral grid outside grid and boundary layer.If the minimum volume of any volume mesh is more than zero, the grid model of the canard configuration aircraft is obtained.
- 4. according to the method for claim 3, it is characterised in that the threedimensional model to the canard configuration aircraft The outer surface in flow field domain carries out mesh generation respectively corresponding to the threedimensional model of surface and the canard configuration aircraft, obtains three The surface grids on the overseas surface of the surface grids on dimension module surface and flow field include：When carrying out mesh generation to the surface grids on the threedimensional model surface, set the full-size of projectile nose surface grids as 15mm, the full-size of duck rudder face grid are 6mm, and the full-size of body surface grids is 20mm, the maximum chi of empennage surface grids Very little is 8mm；When the surface grids to the overseas surface in the flow field carry out mesh generation, the surface grids size on the overseas surface in flow field is set most Greatly 1500mm.
- 5. according to the method for claim 1, it is characterised in that the k- ε turbulent flow mathematical modelings are specially：Establish on the basis of the eddy viscosity assumption of isotropy,Tubulence energy k equations：<mrow> <mfrac> <mo>&part;</mo> <mrow> <mo>&part;</mo> <mi>t</mi> </mrow> </mfrac> <mrow> <mo>(</mo> <mi>&rho;</mi> <mi>k</mi> <mo>)</mo> </mrow> <mo>+</mo> <mfrac> <mo>&part;</mo> <mrow> <mo>&part;</mo> <msub> <mi>x</mi> <mi>i</mi> </msub> </mrow> </mfrac> <mrow> <mo>(</mo> <msub> <mi>&rho;ku</mi> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>=</mo> <mfrac> <mo>&part;</mo> <mrow> <mo>&part;</mo> <msub> <mi>x</mi> <mi>j</mi> </msub> </mrow> </mfrac> <mo>&lsqb;</mo> <mrow> <mo>(</mo> <mi>&mu;</mi> <mo>+</mo> <mfrac> <msub> <mi>&mu;</mi> <mi>t</mi> </msub> <msub> <mi>&sigma;</mi> <mi>k</mi> </msub> </mfrac> <mo>)</mo> </mrow> <mfrac> <mrow> <mo>&part;</mo> <mi>k</mi> </mrow> <mrow> <mo>&part;</mo> <msub> <mi>x</mi> <mi>j</mi> </msub> </mrow> </mfrac> <mo>&rsqb;</mo> <mo>+</mo> <msub> <mi>G</mi> <mi>k</mi> </msub> <mo>+</mo> <msub> <mi>G</mi> <mi>b</mi> </msub> <mo>-</mo> <mi>&rho;</mi> <mi>&epsiv;</mi> <mo>-</mo> <msub> <mi>Y</mi> <mi>M</mi> </msub> <mo>+</mo> <msub> <mi>S</mi> <mi>k</mi> </msub> <mo>;</mo> </mrow>The rule that dissipates ε equations：<mrow> <mfrac> <mo>&part;</mo> <mrow> <mo>&part;</mo> <mi>t</mi> </mrow> </mfrac> <mrow> <mo>(</mo> <mi>&rho;</mi> <mi>&epsiv;</mi> <mo>)</mo> </mrow> <mo>+</mo> <mfrac> <mrow> <mo>&part;</mo> <mi>&epsiv;</mi> </mrow> <mrow> <mo>&part;</mo> <msub> <mi>x</mi> <mi>i</mi> </msub> </mrow> </mfrac> <mrow> <mo>(</mo> <msub> <mi>&rho;&epsiv;u</mi> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>=</mo> <mfrac> <mo>&part;</mo> <mrow> <mo>&part;</mo> <msub> <mi>x</mi> <mi>j</mi> </msub> </mrow> </mfrac> <mo>&lsqb;</mo> <mrow> <mo>(</mo> <mi>&mu;</mi> <mo>+</mo> <mfrac> <msub> <mi>&mu;</mi> <mi>t</mi> </msub> <msub> <mi>&sigma;</mi> <mi>&epsiv;</mi> </msub> </mfrac> <mo>)</mo> </mrow> <mfrac> <mrow> <mo>&part;</mo> <mi>&epsiv;</mi> </mrow> <mrow> <mo>&part;</mo> <msub> <mi>x</mi> <mi>j</mi> </msub> </mrow> </mfrac> <mo>&rsqb;</mo> <mo>+</mo> <msub> <mi>C</mi> <mrow> <mn>1</mn> <mi>&epsiv;</mi> </mrow> </msub> <mfrac> <mi>&epsiv;</mi> <mi>k</mi> </mfrac> <mrow> <mo>(</mo> <msub> <mi>G</mi> <mi>k</mi> </msub> <mo>+</mo> <msub> <mi>C</mi> <mrow> <mn>3</mn> <mi>&epsiv;</mi> </mrow> </msub> <msub> <mi>G</mi> <mi>b</mi> </msub> <mo>)</mo> </mrow> <mo>-</mo> <msub> <mi>C</mi> <mrow> <mn>2</mn> <mi>&epsiv;</mi> </mrow> </msub> <mi>&rho;</mi> <mfrac> <msup> <mi>&epsiv;</mi> <mn>2</mn> </msup> <mi>k</mi> </mfrac> <mo>+</mo> <msub> <mi>S</mi> <mi>&epsiv;</mi> </msub> <mo>;</mo> </mrow>In formula：K is tubulence energy, and t represents time, ρ gas densities, and μ is molecular viscosity coefficient, turbulent viscosityCμ= 0.0845, xiAnd xjDenotation coordination component, ε are tubulence energy dissipative shock wave respectively, GkAnd GbRespectively by local velocity gradient and wind-force Caused tubulence energy generating item, YMFor the dissipative shock wave that expansion fluctuation is formed in compressible turbulent flow, C1ε、C2ε、C3εFor empirical, Respectively C1ε=1.5, C2ε=2.1, G3ε=0.1, σkAnd σεThe respectively turbulent prandtl number corresponding with k and ε, respectively σk =1.1, σε=1.4, SkAnd SεFor customized source item, respectively Sk=Sε=0.
- 6. according to the method for claim 1, it is characterised in that it is described by the k- ε turbulent flows mathematical modeling to the duck The aerodynamic parameter of formula layout aircraft, which carries out analog approach, to be included：The three-dimensional solver based on the implicit stable state of density is set；The primary condition and boundary condition of the grid model of the canard configuration aircraft are set；The solution control parameter of the k- ε turbulent flow mathematical modelings is set：Convergence is 10-5, iterations 5000；By the solution control parameter of setting to the k- ε turbulent flows mathematical modeling iterative, the flow velocity of turbulent motion is obtained, and The aerodynamic force and torque of canard configuration aircraft are obtained by the flow relocity calculation of the turbulent motion.
- 7. according to the method for claim 6, it is characterised in that the grid model that the canard configuration aircraft is set Primary condition and boundary condition include：The external boundary condition for setting the flow field domain is pressure far field；Air pressure inside the flow field domain is arranged to 101325pa, and the temperature setting inside the domain of flow field is 300K, inside the domain of flow field Flowing material be perfect gas；The boundary condition on the surface of the canard configuration aircraft is arranged to stable without sliding wall, the rotation in the flow field domain Rotating speed is set to 0rad/s.
- A kind of 8. terminal device, it is characterised in that including：Model construction module, for building the threedimensional model of canard configuration aircraft；Mesh generation module, flown for the surface of the threedimensional model to the canard configuration aircraft and the canard configuration The outer surface in flow field domain corresponding to the threedimensional model of device carries out mesh generation, according to the grid on the threedimensional model surface and flow field The grid on overseas surface obtains the volume mesh in the flow field domain, and the volume mesh is the grid mould of the canard configuration aircraft Type；Turbulence model creation module, for establishing the k- ε turbulent flow mathematics simulated to the air flow inside the volume mesh Model；Aerodynamic parameter analog module, for the pneumatic ginseng by the k- ε turbulent flows mathematical modeling to the canard configuration aircraft Number carries out analog approach.
- 9. a kind of terminal device, including memory, processor and it is stored in the memory and can be on the processor The computer program of operation, it is characterised in that realize such as claim 1 to 7 described in the computing device during computer program The step of any one methods described.
- 10. a kind of computer-readable recording medium, the computer-readable recording medium storage has computer program, and its feature exists In when the computer program is executed by processor the step of realization such as any one of claim 1 to 7 methods described.
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| CN112270046A (en) * | 2020-11-09 | 2021-01-26 | 北京机电工程研究所 | Method for simulating separation track of protective cover of air inlet channel |
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| CN113551565A (en) * | 2021-09-18 | 2021-10-26 | 中国科学院力学研究所 | Stage section pneumatic shape-preserving solid rocket and separation method |
| CN113551565B (en) * | 2021-09-18 | 2021-11-30 | 中国科学院力学研究所 | Stage section pneumatic shape-preserving solid rocket and separation method |
| CN114595647A (en) * | 2022-05-10 | 2022-06-07 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Magnetic levitation flight wind tunnel pneumatic structure coupling simulation evaluation method |
| CN114595647B (en) * | 2022-05-10 | 2022-08-02 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Magnetic levitation flight wind tunnel pneumatic structure coupling simulation evaluation method |
| CN115057001A (en) * | 2022-08-17 | 2022-09-16 | 中国空气动力研究与发展中心空天技术研究所 | Grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method |
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